Force hub sensor for control wheel steering

ABSTRACT

A two-axis force sensor with minimal space requirements is constructed of concentric sleeve members between which a single ring-like elastic member provides a spring restrained coupling as to both relative rotation and axial translation between the sleeve members. Force readout means may comprise strain gauges attached to the coupling member per se or other transducer means responsive to relative motion between sleeves from rest position.

United States Patent White [54] FORCE HUB SENS-0R FOR CONTROL WHEELSTEERING I [72] Inventor: Kenneth H. White, Marion, Iowa [73] Assignee:Collins Radio Company, Cedar Rapids, Iowa [22] Filed: Dec. 14, 1970 21'Appl. No.: 97,556

[52] US. Cl....' ..73/136C [51] Int. Cl. ..G0ll 5/22 [58] Field ofSearch ..73/136 B, 136 C, 136 A [56] References Cited UNITED STATESPATENTS 1,204,292 11/1916 'McCormick ..73/136 A 2,592,796 4/1952Doussain ..73/136 C [15] 3,705,530 [451 Dec. 12, 1972 7/1946 Ruge..73/136C 9/1939 Muir ..73/136C Primary Examiner-Jerry W. MyracleAttorneyRichard W. Anderson and Robert J. Crawford [57] ABSTRACT Atwo-axis force sensor with minimal space requirements is constructed ofconcentric sleeve members between which a single ring-like elasticmember provides a spring restrained coupling as to both relativerotation and axial translation between the sleeve members.'Force readoutmeans may comprise strain gauges attached to the coupling member per seor other transducer means responsive to relative motion between sleevesfrom rest position. v

17 Claims, 6 Drawing Figures PATENTEU EII 12 I972 3.705.530

- sum 1 [if 2 t s m N 8 E ||||l||l (\l N L a J INVENTOR 8 KENNETH H.WHITE AGENT PATENTED UEIJ 12 I972 SHEET 2 0F 2 INVENTOR KENNETH HL-aWHITE FIG.

AGENT 'for the purpose of detecting pilot applied control forces.

The sensor of the present invention is especially useful for employmentin an aircraft control system wherein pilot applied forces may bedetected by electromechanical transducers for use in effecting aircraftcontrol rates as a function of the forces applied.

For this purpose, two-axis sensors have been developed in the art bymeans of which the forces applied during pilot aileron control appliedforces (bank) and the forces applied laterally in the form of elevatorcontrol forces (pitch) may be transduced into electrical signals forapplication to automatic control circuitry to command the aircraftelevator and aileron control systems in proportion therewith.

Known sensors to provide this function generally take the form of acoupling between the control wheel and the control column which permitslimited relative rotation between the wheel and the column against aspring restraint and also limited lateral translation within thecoupling against a further spring restraint. Strain gauges ordisplacement sensors associated with each of the spring restrainingmeans may then be utilized to transduce applied forces into aproportional electrical control signal in either or both of the two axesunder consideration.

Because force sensors of this type become a part of the primary-controlsystem of the aircraft, that is, they are actually a coupling betweenthe control wheel and the control column, rigid strength requirementsare set down in Federal Airworthiness Regulations whichinclude maximumpilot control forces and a minimum factor of safety. In addition, uponfailure of the spring restraining means employed in such devices, only aminimum amount of free play is permissible in the control system.Further, the application of forces beyond a predetermined threshold mustestablish a positive mechanical coupling between control wheel andcolumn.

Because of the stringent regulations, known force sensors are generallyappreciable in size and, as such, not readily compatible with thecontrol wheel and control column dimensions of smaller aircraft.Particularly, the wheel hub of smaller aircraft is of a small diameterwhich does not permit integrating known force sensors within theconfines of the hub proper.

It is accordingly an object of the present invention to provide animproved two-axis force sensor of a type which might be employed inaircraft control systems having minimal space requirements and mayreadily be installed within the control wheel hub or control column ofsmaller aircraft.

A further object of the present invention is to provide a two-axisforcesensor of the type generally described above which is constructedof a minimum of coacting parts and which provides a positive, veryrugged, mechanical stop upon application of forces to either of thecontrol axes of a predetermined threshold.

The present invention is featured in first and second concentric sleevemembers uniquely interconnectedwith a single spring member and acoacting mechanical limit means whereby deflection of the single springmember in the two axes under consideration may be readily detected toprovide output sensors with indications of the forces exerted in eitheror both of the two axes.

These and other objects and features of the present invention willbecome apparent upon reading the following description with reference tothe accompanying drawings in which:

FIG. 1 is a partial section plan view of a force sensor mechanism inaccordance with the present invention.

FIG. 2 is a cross section detail of the force sensor.

FIG. 3 is a functional isometric view of the interrela tionship betweenthe spring member and sleeve members of a sensor in accordance with thepresent invention;

FIG. 4 illustrates the spring coupling and sensing means member of thepresent invention;

FIG. 5 is a mechanical detail of the interrelationship of the memberseffecting a positive mechanical limit; and

FIG. 6 is a diagrammatic representation of an aircraft control wheel andcolumn with functional inclusion of a force sensor as described in thepresent invention.

As above-described, the mechanism of the present invention may beemployed as an input member for a control wheel steering system in anaircraft. As such, the mechanism is interposed as a coupling between thecontrol wheel and the control system to sense pilot applied elevator andaileron control forces.

It is highly advantageous for such sensors to be placed within thecontrol wheel hub per se or, alternatively, as close to this location asgood design practice permits, in order to avoid placing the controlcolumn inertia between the pilot and the sensor.

The transducer of the present invention lends itself to extremecompactness in design and thus is uniquely compatible with control wheelhub integrated installations. The sensor to be described consistsgenerally of an inner sleeve member which might be coupled to theaircraft control column and an outer sleeve member which might besecured to the control wheel. The two sleeves are connected together bya single spring assembly for provision of force measurements within therange of interest defined by a particular control system, and areconnected together by an extremely rugged stop assembly duringapplication of force levels beyond the range of interest. Concentricityof the two sleeve members is established and maintained by a ballbearing assembly at each end of the force sensor assembly. Deflection ofthe spring in response to force application may be measured by one orboth of strain gauge displacement pick-offs associated with the springmember as applicable, or, alternatively, other transducer expedients maybe employed to respond to relative motion between the sleeve members.

Since the force sensor, as above-mentioned, is a part of the primarycontrol system of the aircraft, the force sensor of the presentinvention permits a maximum spring stress far less than the yieldstrength of the elastic material from which the spring is embodied inorder to assure improbability of an endurance failure.

If, however, a spring should break or fail, the sensor mechanism of thepresent invention couples control forces, as exerted by the pilot on thewheel, directly through the sensor in a manner which results in barelymore than a detectable amount of free-play in the control system.

With reference to FIGS. 1, 2, and 3, the force hub sensor in accordancewith the present invention is comprised basically of a pair ofconcentric sleeve members the inner one of which may be coupled to theaircraft control column and the outer one of which may be secured to thecontrol wheel. As will be further described, the mechanism of thepresent invention is readily adaptable for incorporation either withinthe hub of a given wheel, or, alternatively, as a separate couplingmember in the control column. Because of the novel concentricrelationship of all parts including the coupling spring member, themechanism permits a wide range of installation fiexiblity.

With reference to FIG. 1, inner sleeve member 11 is maintainedconcentrically within outer sleeve member by first and second ballbearing assemblies 13 and 14 at each end of the sensor mechanism. Ballbearing assemblies 13 and 14 permit concentric rotation of one sleevemember with respect to the other, and, since the races associated withthe ball bearing members 13 and 14 are flat, relative lateraldisplacement between the inner and outer sleeve members 11 and 10 ispermissible. Retaining ring members 15 and 16 confine ball bearing means13 while retainers l7 and 22 confine ball bearing assembly 14. Theseretaining means are seen to permit an axial displacement of the ballbearing mechanisms along the longitudinal axis of the assembly.

The inner sleeve member 11 and the outer sleeve member 10 are coupledtogether by a single spring assembly 12.

With reference to FIG. 4, spring assembly 12 is comprised of an uppermounting pad member 25 and a lower mounting pad member 26 integrallyjoined with annular ring-like segments. As illustrated, the particularspring embodiment depicted in FIG. 4 comprises a first pair of coplanarannular segments 29 and 30 and a second parallel spaced pair of coplanarannular segments 31 and 32 terminated by the diametrically opposedmounting pad members 25 and 26.

The annular coupling segments between the upper and lower mounting padsof the spring structure are of a finite thickness and width inaccordance with predetermined mechanical deformation properties definedby spring material and configuration as desired for a particularembodiment. The undersides of both the top and bottom pad members areextended such that the upper mounting pad 25 has the same inner radiusas the outer radius of inner sleeve member 11, while the lower padmember 26 has the same outer radius as the inner radius of the outersleeve member 10. In assembled relationship, as depicted in FIGS. 1, 2,and 3, a first bolt member may be threadedly received in the wall of theouter sleeve member 10 and into a threaded mounting hole 28 formedthrough the lower mounting pad member 26 of the spring, so as to rigidlyaffix the spring member to the inside wall of the outer cylinder 10. Theouter radius face of the upper mounting pad member 27 is thus seen to beplaced at a radius somewhat less than the inner radius of the outersleeve member 10 and juxtaposed with a through-slot or aperture 9 formedthrough the outer sleeve wall. A stop member 18 having substantially thesame configuration as the upper mounting pad 25 of the ring member 12 isprovided with a mounting hole through which a bolt member 19 isreceivable into threaded mounting hole 27 in the upper mounting pad 25of the spring, and into threaded engagement with the inner sleeve member11. Stop pad 18 is then rigidly affixed to the top pad 25 of the spring12 and concentrically within the confines of the aperture 9 formed inthe outer cylinder wall so as to permit, for example, a 0.010 inchmovement from rest position both laterally and transversely of the axisof the assembly.

As further illustrated in FIG. 5, the pad stop member 18 is seen to beconfined within the aperture 9 formed in the outer sleeve member 10 suchthat 0.010 inch gaps 34-37 exist between stop member and aperture walls.

As depicted in FIG. 1, the inner cylinder member might be formed with alongitudinally extending bore 21 into which is machined a spline socketto accept a male spline formed on the control column. The outer sleevemember 10 might be formed with an annularly extending adapting flange 8to facilitate coupling with the control wheel (not illustrated) suchthat the entire assembly is within the confines of the control wheelhub. It is noted for this particular application that the annular springmember 12 by means of which the inner and outer sleeves 11 and 10 arecoupled and, as will be further described, by means of which therelative forces applied along two axes may be determined by sensingcorresponding spring deflections, permits a compact arrangement with asplined coupling within the hub confines between the assembly and thecontrol column.

The spring member 12 couples the inner and outer sleeve members 11 and10 in a manner permitting relative sleeve rotation over a limited rangewhile additionally permitting relative longitudinal translation betweenthe two members. These two movements are imparted to the sensingmechanism by pilot applied forces to the wheel and against springimparted restraints.

Over a designed range of input forces effecting relative sleeverotation, the spring member 12 is caused to distort within a planetransverse to the longitudinal axis of the mechanism in the manner of acantilever beam defomiing against the restraint imposed by the controlcolumn load.

The application of pilot applied forces to the wheel for elevatorcontrol imparts a longitudinal force to the outer sleeve member againstthe longitudinal restraining force of the control column and thuseffects a translation between the inner and outer sleeve members againstthe spring restraint. During such lateral displacement of the inner andouter sleeve members the annular coupling segments forming the springmember are imparted with a stress along an axis perpendicular to that ofthe aforedescribed force application, since the upper and lower mountingpads 27 and 26 associated with the spring assembly are displaced fromtheir diametrically opposed unloaded position. Again with reference toFIG. 5, a distortion of the spring member along this axis is limited byone or the other of the sides of the stop member 18 engaging a surfaceof the througheslot 9 in outer sleeve member 10.

FIG. 2 illustrates the concentric sleeve members in their assembledrelationship with the spring assembly 12 and indicates that clearance isreadily provided for spring distortion in response to relative rotationbetweenthe sleeve members within the limits defined by the aperture 9formed in the outer sleeve and the stopmember 18.

The assembly thus provides ameans for coupling concentric sleeve membersin a manner permitting limited translational as well as rotationalmovements between the two sleeves and, in addition, in a mannerestablishing a rest position from which the limited relative movementsare restrained. Since the coupling member between the two sleeves is aspring member, the spring material and dimensions establish apredetermined relationship between the relative translational androtational movements between the two sleeves and the force applied toeffect these movements. As such, transducer means may be employed todetect the relative sleeve member motions both in sense and magnitudefrom the established rest position of the sleeves. As illustrated inFIG. 4, strain gauge transducers 38 and 39 might be mounted on theradially extending surfaces of arcuate spring segments and 32 to beutilized in appropriate circuit for detecting forces effecting relativesleeve translation. These members may be attached to the annularsegments at points approximately one-fourth (angle-wise) from either ofthe respective spring anchor points established by spring mounting padmembers 27 and 26. This expedient is employed sincethe cantilever-likeaction of the spring member, as it distorts in response to axial loadingbetween the sleeves, establishes a neutral axis approximately midwaybetween the spring anchor points. As illustrated in FIG. 4, the straingauges 39 and 38 are mounted anglewise 45 down from the location of theupper spring mounting hole 27 to avoid a neutral axis midway betweenmounting points.

A further pair of strain gauges 40 and 41 may be mounted on the outerdiameter surfaces of the arcuate spring segments. As depicted in FIG. 4,gauges 40 and 41 might preferably be mounted on symmetrically oppositecoplanar ones of the arcuate spring segments at points (in order toavoid a neutral axis) one-third (angle-wise) from the bottom mountingpoint established by pad 26.

Spring member 12 as described and illustrated herein is comprised of afirst pair of coplanar arcuate coupling segments paralleled with asecond such pair between upper and lower mounting pads. A single suchpair or a plurality of pairs of coplanar segments might be employed. Theparticular configuration is based solely on the design criteria for agiven embodiment in terms of type of elastic material employed, themaximum stresses to be imparted, the safety factors as against springfailure to be considered, etc. In a general sense the spring member iscomprised of a cantilever beam member embodied as a ring.

FIG. 6 functionally depicts an aircraft control wheel 41 including a hubportion 42 attached to a control column 43 wherein a force sensormechanism 44 in accordance with the present invention may beinterconnected as a coupling member in the column per se, in which casethe section of the column 43 attached to the wheel hub 42 would affix tothe outer sleeve member 10 of the sensor and the control column portionleading to the aircraft control system would be affixed to the innersleeve member 11 of the mechanism. It is to be understood that in thistype of application the outer and inner sleeve members may be formedwith any desired coupling terminations to mate with the column crosssections. In a most advantageous sense the formation of a coupling ringon the outer sleeve which may be mated to the hub per se of a controlwheel (FIG. 1) is preferred because of the desirability of mounting theforce sensor as close to the pilot applied forces as possible to includeas little as possible of the control column and yoke assembly inertiabetween the point of force application and the location of the sensorwith which these forces are detected.

The present invention is thus seen to provide a compact force sensingmechanism of a dual axis type which is comprised of a minimal number ofparts and includes a novel unitary spring coupling and sensing assembly.

Although the present invention has been described with respect toparticular embodiments thereof, it is not to be so limited as changesmight be made therein which fall within the scope of the invention asdefined in the appended claims.

Iclaim:

1. In combination with first and second concentric sleeve members, theinside diameter of the outer one of said sleeve members exceeding theoutside diameter of the inner one of said sleeve members, means forestablishing a predetermined force to mechanical displacement ratiobetween said first and second concentric sleeve members, comprisingbearing means communicating with said sleeve members and mountedtherebetween, said bearing means maintaining concentricity between saidfirst and second sleeve members and permitting both relative rotationabout a rotational axis common to said sleeve members and axialtranslation between said sleeve members along said rotational axis, anannular ring-like elastic member carried within the radial space betweensaid first and second sleeve members, said first and second sleevemembers having respective radial dimensions establishing a predeterminedradial clearance between said elastic member and each of said sleevemembers, said elastic member communicating with first and seconddiametrically opposed mounting surfaces, said mounting surfaces havingrespective radial dimensions establishing juxtaposition of one of saidmounting surfaces with the outer surface of said inner sleeve member andthe other of said mounting surfaces with the inside surface of saidouter sleeve member while maintaining concentricity between said elasticmember and said sleeve members, and means for rigidly affixing saidelastic member mounting surfaces with said respective juxtaposed ones ofsaid inner and outer sleeve member surfaces, whereby said relativerotation and axial translation between said first and second sleevemembers is effected against predetermined restraints imposed by thegeometry and resilient characteristics of said elastic member.

2. Means as defined in claim 1 wherein said elastic member comprises atleast one pair of coplanar annular segments terminated in said first andsecond mounting surfaces, each of said segments being rectangular incross section and having a radially extending dimension generally inexcess of the thickness thereof.

3. Means as defined in claim 1 further comprising mechanical stop meansassociated with said inner sleeve member and cooperating with mechanicalstop limit means associated with said outer sleeve member to establishpredetermined maximum relative rotation and relative translation limitsbetween said first and second sleeve members.

4. Means as defined in claim 3 wherein said mechanical stop meanscomprises a through-aperture formed in said outer sleeve member andgenerally juxtaposed with a first one of said mounting surfacesassociated with said elastic member, the radial dimension of firstelastic member mounting surface being extended to project within theconfines of said through-aperture to establish a predetermined clearancebetween the extreme dimensions of surface extension and the radiallyextending walls of said through-aperture, whereby application of forcesin response to which predetermined rotational and translational limitsare exceeded between said first and second sleeve members effects anabutting communication between said mounting member extension and thewalls of said through-aperture.

5. Means as defined in claim 1 wherein said elastic member comprises aparalleled plurality of coplanar pairs of said annular segments.

6. Means as defined in claim 5 wherein said elastic member and the firstand second mounting surfaces associated therewith are integrally formedfrom a common elastic material.

7. in combination with first and second concentric sleeve members, meansfor measuring forces applied to effect relative rotation about arotational axis common to said sleeve members and axial translation ofsaid first sleeve member with respect to said second sleeve member alongsaid rotational axis comprising means for mounting said second sleevemember concentrically within said first sleeve member, said means formounting establishing a spaced relationship between said sleeve membersand permitting relative rotation and axial translation therebetween,said second sleeve member being connected to a mechanical loadpresenting predetermined forces resisting said rotation and axialtranslation between said sleeve members, an annular ring-like elasticmember carried transverse the longitudinal axes of said sleeve membersand within the radial space therebetween and having dimensionsestablishing radial clearance with said respective sleeve members, saidelastic member communicating with first and second diametrically opposedmounting surfaces the respective radial dimensions of which permitjuxtaposition of one of said mounting surfaces with the outer surface ofsaid inner sleeve member and of the other of said mounting surfaces withthe inside surface of said outer sleeve member while maintainingconcentricity between said elastic member and said first and secondsleeve members, means for rigidly affixing said mounting surfaces withsaid respective juxtaposed ones of said inner and outer sleeve membersurfaces whereby application of forces to said first sleeve membereffecting relative rotation between said sleeve members and axialtranslation between said sleeve members against the restraints of saidelastic member bear a predetermined applied force-to-mechanicaldisplacement ratio defined by the geometry and resilient characteristicsof said elastic member, and transducer means responsive to relativerotation and translation between said sleeve members to establish firstand second output signals respectively proportional to said relativerotation and translation.

8. Means as defined in claim 7 wherein said transducer means comprisesrespective strain gauge means mounted on said elastic member.

9. Means as defined in claim 7 wherein said elastic member comprises atleast one pair of coplanar annular segments terminated in said first andsecond mounting surfaces, each of said segments being rectangular incross section and having a radially extending dimension generally inexcess of the thickness thereof.

10. Means as defined in claim 7 wherein said elastic member comprises aparalleled plurality of coplanar pairs of said annular segments.

11. Means as defined in claim 7 further comprising mechanical stop meansassociated with said inner sleeve member and cooperating with mechanicalstop limit means associated with said outer sleeve member to establishpredetermined maximum relative rotation and relative translation limitsbetween said first and second sleeve members.

12. Means as defined in claim 11 wherein said mechanical stop meanscomprises a through-aperture formed in said outer sleeve member andgenerally juxtaposed with a first one of said mounting surfacesassociated with said elastic member, the radial dimension of firstelastic member mounting surface being extended to project within theconfines of said throughaperture to establish a predetermined clearancebetween the extreme dimensions of surface extension and the radiallyextending walls of said through-aperture, whereby application of forcesin response to which predetermined rotational and translational limitsare exceeded between said first and second sleeve members effects anabutting communication between said mounting member extension and thewalls of said through-aperture.

13. Means as defined in claim 12 wherein said transducer means comprisesrespective strain gauge means mounted on said elastic member.

14. Means as defined in claim 12 wherein said elastic member comprisesat least one pair of coplanar annular segments terminated in said firstand second mounting surfaces, each of said segments being rectangular incross section and having a radially extending dimension generally inexcess of the thickness thereof.

15. Means as defined in claim 14 wherein said elastic member and thefirst and second mounting surfaces associated therewith are integrallyformed from a common elastic material.

16. Means as defined in claim 12 wherein said elastic member comprises aparalleled plurality of coplanar pairs of said annular segments.

17. Means as defined in claim 16 wherein said elastic member and thefirst and second mounting surfaces associated therewith are integrallyformed from a common elastic material.

1. In combination with first and second concentric sleeve members, theinside diameter of the outer one of said sleeve members exceeding theoutside diameter of the inner one of said sleeve members, means forestablishing a predetermined force to mechanical displacement ratiobetween said first and second concentric sleeve members, comprisingbearing means communicating with said sleeve members and mountedtherebetween, said bearing means maintaining concentricity between saidfirst and second sleeve members and permitting both relative rotationabout a rotational axis common to said sleeve members and axialtranslation between said sleeve members along said rotational axis, anannular ring-like elastic member carried within the radial space betweensaid first and second sleeve members, said first and second sleevemembers having respective radial dimensions establishing a predeterminedradial clearance between said elastic member and each of said sleevemembers, said elastic member communicating with first and seconddiametrically opposed mounting surfaces, said mounting surfaces havingrespective radial dimensions establishing juxtaposition of one of saidmounting surfaces with the outer surface of said inner sleeve member andthe other of said mounting surfaces with the inside surface of saidouter sleeve member while maintaining concentricity between said elasticmember and said sleeve members, and means for rigidly affixing saidelastic member mounting surfaces with said respective juxtaposed ones ofsaid inner and outer sleeve member surfaces, whereby said relativerotation and axial translation between said first and second sleevemembers is effected against predetermined restraints imposed by thegeometry and resilient characteristics of said elastic member.
 2. Meansas defined in claim 1 wherein said elastic member comprises at least onepair of coplanar annular segments terminated in said first and secondmounting surfaces, each of said segments being rectangular in crosssection and having a radially extending dimension generally in excess ofthe thickness thereof.
 3. Means as defined in claim 1 further comprisingmechanical stop means associated with said inner sleeve member andcooperating with mechanical stop limit means associated with said outersleeve member to establish predetermined maximum relative rotation andrelative translation limits between said first and second sleevemembers.
 4. Means as defined in claim 3 wherein said mechanical stopmeans comprises a through-aperture formed in said outer sleeve memberand generally juxtaposed with a first one of said mounting surfacesassociated with said elastic member, the radial dimension of firstelastic member mounting surface being extended to project within theconfines of said through-aperture to establish a predetermined clearancebetween the extreme dimensions of surface extension and the radiallyextending walls of said through-aperture, whereby application of forcesin response to which predetermined rotational and translational limitsare exceeded between said first and second sleeve members effects anabutting communication between said mounting member extension and thewalls of said through-aperture.
 5. Means as defined in claim 1 whereinsaid elastic member comprises a paralleled plurality of coplanar pairsof said annular segments.
 6. Means as defined in claim 5 wherein saidelastic member and the first and second mounting surfaces associatedtherewith are integrally formed from a common elastic material.
 7. Incombination with first and second concentric sleeve members, means formeasuring forces applied to effect relative rotation about a rotationalaxis common to said sleeve members and axial translation of said firstsleeve member with respect to said second sleeve member along saidrotational axis comprising means for mounting said second sleeve memberconcentrically within said first sleeve member, said means for mountingestablishing a spaced relationship between said sleeve members andpermitting relative rotation and axial translation therebetween, saidsecond sleeve member being connected to a mechanical load presentingpredetermined forces resisting said rotation and axial translationbetween said sleeve members, an annular ring-like elastic member carriedtransverse the longitudinal axes of said sleeve members and within theradial space therebetween and having dimensions establishing radialclearance with said respective sleeve members, said elastic membercommunicating with first and second diametrically opposed mountingsurfaces the respective radial dimensions of which permit juxtapositionof one of said mounting surfaces with the outer surface of said innersleeve member and of the other of said mounting surfaces with the insidesurface of said outer sleeve member while maintaining concentricitybetween said elastic member and said first and second sleeve members,means for rigidly affixing said mounting surfaces with said respectivejuxtaposed ones of said inner and outer sleeve member surfaces wherebyapplication of forces to said first sleeve member effecting relativerotation between said sleeve members and axial translation between saidsleeve members against the restraints of said elastic member bear apredetermined applied force-to-mechanical displacement rAtio defined bythe geometry and resilient characteristics of said elastic member, andtransducer means responsive to relative rotation and translation betweensaid sleeve members to establish first and second output signalsrespectively proportional to said relative rotation and translation. 8.Means as defined in claim 7 wherein said transducer means comprisesrespective strain gauge means mounted on said elastic member.
 9. Meansas defined in claim 7 wherein said elastic member comprises at least onepair of coplanar annular segments terminated in said first and secondmounting surfaces, each of said segments being rectangular in crosssection and having a radially extending dimension generally in excess ofthe thickness thereof.
 10. Means as defined in claim 7 wherein saidelastic member comprises a paralleled plurality of coplanar pairs ofsaid annular segments.
 11. Means as defined in claim 7 furthercomprising mechanical stop means associated with said inner sleevemember and cooperating with mechanical stop limit means associated withsaid outer sleeve member to establish predetermined maximum relativerotation and relative translation limits between said first and secondsleeve members.
 12. Means as defined in claim 11 wherein said mechanicalstop means comprises a through-aperture formed in said outer sleevemember and generally juxtaposed with a first one of said mountingsurfaces associated with said elastic member, the radial dimension offirst elastic member mounting surface being extended to project withinthe confines of said through-aperture to establish a predeterminedclearance between the extreme dimensions of surface extension and theradially extending walls of said through-aperture, whereby applicationof forces in response to which predetermined rotational andtranslational limits are exceeded between said first and second sleevemembers effects an abutting communication between said mounting memberextension and the walls of said through-aperture.
 13. Means as definedin claim 12 wherein said transducer means comprises respective straingauge means mounted on said elastic member.
 14. Means as defined inclaim 12 wherein said elastic member comprises at least one pair ofcoplanar annular segments terminated in said first and second mountingsurfaces, each of said segments being rectangular in cross section andhaving a radially extending dimension generally in excess of thethickness thereof.
 15. Means as defined in claim 14 wherein said elasticmember and the first and second mounting surfaces associated therewithare integrally formed from a common elastic material.
 16. Means asdefined in claim 12 wherein said elastic member comprises a paralleledplurality of coplanar pairs of said annular segments.
 17. Means asdefined in claim 16 wherein said elastic member and the first and secondmounting surfaces associated therewith are integrally formed from acommon elastic material.